# Bombardier Service Bulletin 55-27-41

Copy: No revision named ("SB 55-27-41"), 46 pages: PDF https://openairdocs.org/files/sha256/57/5d/575d55992fb1c11879d7cc3e534ecfb3ffd6c21b0ae98124b90adcc77c58475b; text https://openairdocs.org/service-documents/bombardier/sb-55-27-41/file/575d55992fb1.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2018-0327; AD 2018-19-04 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Bombardier](https://openairdocs.org/service-documents/bombardier.md)
- Type: Service bulletin (Service Bulletin)
- Number: 55-27-41
- Page: https://openairdocs.org/service-documents/bombardier/sb-55-27-41

## ADs that cite it (1) (OpenAirDocs)

Newest first, with the revision each names, as OpenAirDocs read it from the AD's text.

- [AD 2018-19-04](https://openairdocs.org/ad/2018-19-04.md), effective Oct 23, 2018: No revision named

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/bombardier/sb-55-27-41/proposed.md).

## Text (46 pages)

Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2018-0327; AD 2018-19-04 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

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Refer to applicable government agency regulations and requirements and make sure that the work described 
in this publication is performed in compliance with manufacturer’s recommendations and/or acceptable industry standards. 
This document is proprietary to Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or by 
any means without the prior written consent of Bombardier Inc. and/or its affiliates. 
© 2017, Bombardier Inc. All rights reserved. 
Challenger*, Global Express*, Learjet*, are Trademarks of Bombardier Inc.
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Basic Issue: Sep 11/17
Contact Information Distribution Date
Business Aircraft 
Learjet Inc.
MS 53
P.O. Box 7707
Wichita, Kansas 67277-7707
Customer Response Center (CRC)
AC.ICT@aero.bombardier.com
1-866-538-1247 (Toll Free)
1-514-855-2999 (Tel)
Push 5 then 2 for Parts Services or push 4 
then 2 for Technical Publications.
September 11, 2017
LEARJET 55
If the instructions in this publication cannot be completed because of an STC change to the aircraft, speak to
the STC holder or the regional Federal Aviation Administration (FAA) office for information and disposition.
Service Bulletin
These commodities, technology or software were exported from the United States in accordance
with the Export Administration Regulations. Diversion contrary to United States law is prohibited.
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 2
FLIGHT CONTROLS - FLAP STRUCTURE MODIFICATION
1. Planning Information
A. Effectivity
(1) Learjet 55-003 thru 55-147.
B. Reason
(1) The purpose of this service bulletin is to replace the nose roller fitting, nose roller support bracket,
and adjacent rib support structure with more robust components at all four locations where they
were not previously replaced by Service Bulletin 55-27-32, "Inspection/Installation of Flap Struc-
ture Components", Basic issue or Revisions 1, 2, 3 or 4.
C. Description
(1) This service bulletin supplies instructions to replace the nose roller fitting, nose roller support
bracket, and adjacent rib support structure with more robust components at all four locations
where they were not previously replaced by Service Bulletin 55-27-32, "Inspection/Installation of
Flap Structure Components", Basic issue or Revisions 1, 2, 3, or 4.

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Service Bulletin
D. Compliance
(1) Recommended - Bombardier Learjet Inc. recommends these instructions are completed within 24
months or 400 landings (whichever comes first) from the initial distribution date of this publication.
E. Approval
(1) The Federal Aviation Administration (FAA) has approved the technical content in this publication
that has an effect on the airplane type design.
(2) The European Aviation Safety Agency (EASA) has accepted the technical content in this publica-
tion that has an effect on the airplane type design.
(3) T ransport Canada Civil Aviation (TCCA) has accepted the technical content in this publication that
has an effect on the airplane type design.
F . Labor Hours - Estimated Accomplishment Time
NOTE: The labor hours provided are estimates to assist scheduling and planning the tasks given
in this bulletin. The estimates are for direct labor performed by an experienced crew and
do not include the time for familiarization, planning, aircraft preparation in hangar, such as
towing and positioning of scaffolds, removal of aircraft loose equipment, acquisition of
tools and equipment, training, supervision and inspection.
If labor coverage is provided, only the hours above will be paid.
When planning to complete these instructions, please contact Bombardier Aerospace,
Learjet Inc. Business Aircraft Customer Service, Parts Services for parts availability and
shipping times as necessary . (Refer to the title page of this document for contact
information.)
G. Expense Coverage
(1) Labor Coverage - None.
(2) Material Coverage - None.
LABOR 
HOURS TASK
8.0 Labor hours to gain access.
158.0 Labor hours to do the aircraft modification.
21.0 Labor hours to do a functional test/operational check.
1.0 Labor hours to return the aircraft to airworthy status.
188.0 Total Labor Hours

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LEARJET 55
Service Bulletin
H. Material Required
NOTE: For current prices, availability , ordering and shipping information, please call Bombardier
Aerospace, Learjet Inc. Business Aircraft Customer Service, Parts Services. (Refer to the
title page of this document for contact information.)
Refer to Paragraph 2.A. to know which kit is necessary .
(1) Other materials/parts necessary to complete these instructions.
NOTE: For ordering and shipping information, please contact Bombardier Aerospace, Learjet
Inc., Business Aircraft Customer Service, Parts Logistics. (Refer to the title page of
this document for contact information.)
PART NUMBER QTY NOMENCLATURE
2381000-802 1 Service Bulletin Kit
2381000-804 1 Service Bulletin Kit
2381000-809 1 Service Bulletin Kit
2381000-810 1 Service Bulletin Kit
2381000-817 1 Service Bulletin Kit
2381000-818 1 Service Bulletin Kit
2381000-819 1 Service Bulletin Kit
2381000-820 1 Service Bulletin Kit
2381000-821 1 Service Bulletin Kit
PART NUMBER NOMENCLATURE QTY SUPPLIER
Hysol EA 9602.3
or
Class II
(Refer to Chapter 20 of the 
Maintenance Manual .)
Adhesive film
or
Adhesive
As 
Required Obtain Locally
Clear Polyurethane 
Protective Coating
As 
Required Obtain Locally

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Basic Issue: Sep 11/17
LEARJET 55
Service Bulletin
I. T ools, Equipment and Materials
(1) Refer to Chapter 20 of the Maintenance Manual for standard shop practice tools/equipment
required.
(2) Refer to "T ools and Equipment" in the Removal/Installation of the Flaps section in Chapter 27 of
the Maintenance Manual .
NOTE: Other tools and equipment may be necessary based on individual aircraft require-
ments, facility and personnel capabilities.
J. Weight and Balance
(1) Change in basic weight and moment.
K. References
NOTE: If applicable, referenced third party documentation can be accessed from the Customer
Portal under this service bulletin number.
(1) Service Bulletin Compliance Response Form.
(2) Service Bulletin Evaluation Sheet.
(3) Learjet Maintenance Manual, Chapters 20, 24, and 27.
(4) Learjet Structural Repair Manual, Chapter 51.
(5) FAA Approved Learjet Flight Manual.
L. Other Publications Affected
(1) Learjet Illustrated Parts Catalog, Chapter 27.
KIT CHANGE IN BASIC WEIGHT CHANGE IN BASIC MOMENT
2381000-802 Plus (+) 0.18 pounds Plus (+) 77.0 in-lbs
2381000-804 Plus (+) 0.18 pounds Plus (+) 77.0 in-lbs
2381000-809 Plus (+) 0.18 pounds Plus (+) 76.0 in-lbs
2381000-810 Plus (+) 0.18 pounds Plus (+) 76.0 in-lbs
2381000-817 Negligible Negligible
2381000-818 Plus (+) 0.33 pounds Plus (+) 141.0 in-lbs
2381000-819 Plus (+) 0.33 pounds Plus (+) 141.0 in-lbs
2381000-820 Plus (+) 0.30 pounds Plus (+) 126.0 in-lbs
2381000-821 Plus (+) 0.30 pounds Plus (+) 126.0 in-lbs

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Service Bulletin
2. Material Information
A. Parts Required
NOTE: The determination as to which kit (or kits) is required is based on previous kit installations.
Refer to Service Bulletin 55-27-32, "Inspection/Installation of Flap Structure Components".
(Refer to aircraft maintenance records for record of modified flap components or contact
Bombardier Aerospace, Learjet Inc., Business Aircraft Customer Response Center (CRC).
Refer to the title page of this document for contact information.)
(1) The 2381000-802 kit is effective for all aircraft and contains the parts that follow:
NOTE: The 2381000-802 kit replaces the LH outboard flap track roller fitting.
NOTE: Some hardware comes in pre-packaged quantities. When that occurs,
the quantity in the kit will be more than the quantity in the parts list.
PART 
NUMBER QTY NOMENCLATURE ALTERNATE PART NUMBER
AN3-5A 3 Bolt
AN960-10L 8 Washer
CR3213-5-03 9 Rivet, Blind
CR3243-5-03 3 Rivet, Blind
CR3522-5-05 7 Rivet, Blind
CR3524-5-04 1 Rivet, Blind
CR3524-5-05 6 Rivet, Blind
CSR902B-5-5 1 Rivet, 100 ° Csk Head MS20426T5-5
CSR902B-5-7 4 Rivet, 100 ° Csk Head
CSR904B-5-4 1 Rivet, 100 ° Csk Head
CSR904B-5-5 7 Rivet, 100 ° Csk Head
CSR904B-5-7 8 Rivet, 100 ° Csk Head
MS21042L3 3 Nut
NAS1097AD4-5 25 Rivet, Shear Head
NAS1097AD4-7 6 Rivet, Shear Head
6025021-801 1 Roller Fitting, LH Outboard Flap Track

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Service Bulletin
(2) The 2381000-804 kit is effective for all aircraft and contains the parts as follows:
NOTE: The 2381000-804 kit replaces the RH outboard flap track roller fitting.
NOTE: Some hardware comes in pre-packaged quantities. When that occurs,
the quantity in the kit will be more than the quantity in the parts list.
PART 
NUMBER QTY NOMENCLATURE ALTERNATE PART NUMBER
AN3-5A 3 Bolt
AN960-10L 8 Washer
CR3213-5-03 9 Rivet, Blind
CR3243-5-03 3 Rivet, Blind
CR3522-5-05 7 Rivet, Blind
CR3524-5-04 1 Rivet, Blind
CR3524-5-05 6 Rivet, Blind
CSR902B-5-5 1 Rivet, 100 ° Csk Head MS20426T5-5
CSR902B-5-7 4 Rivet, 100 ° Csk Head
CSR904B-5-4 1 Rivet, 100 ° Csk Head
CSR904B-5-5 7 Rivet, 100 ° Csk Head
CSR904B-5-7 8 Rivet, 100 ° Csk Head
MS21042L3 3 Nut
NAS1097AD4-5 25 Rivet, Shear Head
NAS1097AD4-7 6 Rivet, Shear Head
6025021-802 1 Roller Fitting, RH Outboard Flap Track

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Service Bulletin
(3) The 2381000-809 kit is effective for all aircraft and contains the parts as follows:
NOTE: The 2381000-809 kit replaces the LH inboard flap track roller fitting.
NOTE: Some hardware comes in pre-packaged quantities. When that occurs,
the quantity in the kit will be more than the quantity in the parts list.
PART NUMBER QTY NOMENCLATURE
AN3-5A 3 Bolt
AN960-10L 8 Washer
CR3213-5-03 9 Rivet, Blind
CR3243-5-03 3 Rivet, Blind
CR3522-5-05 7 Rivet, Blind
CR3524-4-04 2 Rivet, Blind
CR3524-5-05 6 Rivet, Blind
CSR902B-5-7 4 Rivet, 100 ° Csk Head
CSR904B-5-5 7 Rivet, 100 ° Csk Head
CSR904B-5-7 8 Rivet, 100 ° Csk Head
MS21042L3 3 Nut
NAS1097AD4-5 25 Rivet, Shear Head
NAS1097AD4-7 7 Rivet, Shear Head
6025022-809 1 Roller Fitting, LH Inboard Flap Track

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LEARJET 55
Service Bulletin
(4) The 2381000-810 kit is effective for all aircraft and contains the parts as follows:
NOTE: The 2381000-810 kit replaces the RH inboard flap track roller fitting.
NOTE: Some hardware comes in pre-packaged quantities. When that occurs,
the quantity in the kit will be more than the quantity in the parts list.
PART NUMBER QTY NOMENCLATURE
AN3-5A 3 Nut
AN960-10L 8 Washer
CR3213-5-03 9 Rivet, Blind
CR3243-5-03 3 Rivet, Blind
CR3522-5-05 7 Rivet, Blind
CR3524-4-04 2 Rivet, Blind
CR3524-5-05 6 Rivet, Blind
CSR902B-5-7 4 Rivet, 100 ° Csk Head
CSR904B-5-5 7 Rivet, 100 ° Csk Head
CSR904B-5-7 8 Rivet, 100 ° Csk Head
MS21042L3 3 Nut
NAS1097AD4-5 25 Rivet, Shear Head
NAS1097AD4-7 7 Rivet, Shear Head
6025022-810 1 Roller Fitting, RH Inboard Flap Track

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LEARJET 55
Service Bulletin
(5) The 2381000-818 kit is effective for all aircraft and contains the parts as follows:
NOTE: The 2381000-818 kit replaces the LH outboard flap roller rib and
nose roller support rib assembly .
NOTE: Some hardware comes in pre-packaged quantities. When that occurs,
the quantity in the kit will be more than the quantity in the parts list.
PART 
NUMBER QTY NOMENCLATURE ALTERNATE PART NUMBER
AN960-616L 2 Washer
CR3242-4-02 145 Rivet, Blind
CR3242-4-03 15 Rivet, Blind
CR3242-4-04 2 Rivet, Blind
CR3243-4-04 3 Rivet, Blind
CSR904B-5-3 1 Rivet, 100 ° Csk Head
CSR904B-5-5 2 Rivet, 100 ° Csk Head
MS14145-4 1 Nut MS14145L4
MS20470AD5-5 2 Rivet
MS20470B3-5 30 Rivet
MS20470B3-7 30 Rivet
MS24665-134 1 Cotter Pin
NAS1097AD4-5 6 Rivet, Shear Head
NAS1097AD5-5 10 Rivet, Shear Head
NAS334CP16 1 Bolt
NAS43DD4-30 1 Spacer
NAS43DD4-30N 
or 
NAS43DD4-30FC
NAS76A4-20 1 Bushing
2325000-13 1 Roller, Nose
2381000-813 1 Rib Assembly, LH Outboard Nose Roller Support
6025028-803 1 Rib, LH Outboard Flap Roller

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LEARJET 55
Service Bulletin
(6) The 2381000-819 kit is effective for all aircraft and contains the parts as follows:
NOTE: The 2381000-819 kit replaces the RH outboard flap roller rib and
nose roller support rib assembly .
NOTE: Some hardware comes in pre-packaged quantities. When that occurs,
the quantity in the kit will be more than the quantity in the parts list.
PART 
NUMBER QTY NOMENCLATURE ALTERNATE PART NUMBER
AN960-616L 2 Washer
CR3242-4-02 145 Rivet, Blind
CR3242-4-03 15 Rivet, Blind
CR3242-4-04 2 Rivet, Blind
CR3243-4-04 3 Rivet, Blind
CSR904B-5-3 1 Rivet, 100 ° Csk Head
CSR904B-5-5 2 Rivet, 100 ° Csk Head
MS14145-4 1 Nut MS14145L4
MS20470AD5-5 2 Rivet
MS20470B3-5 30 Rivet
MS20470B3-7 30 Rivet
MS24665-134 1 Cotter Pin
NAS1097AD4-5 6 Rivet, Shear Head
NAS1097AD5-5 10 Rivet, Shear Head
NAS334CP16 1 Bolt
NAS43DD4-30 1 Spacer
NAS43DD4-30N 
or 
NAS43DD4-30FC
NAS76A4-20 1 Bushing
2325000-13 1 Roller, Nose
2381000-814 1 Rib Assembly, RH Outboard Nose Roller Support
6025028-804 1 Rib, RH Outboard Flap Roller

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Service Bulletin
(7) The 2381000-820 kit is effective for all aircraft and contains the parts as follows:
NOTE: The 2381000-820 kit replaces the LH inboard flap roller rib and
nose roller support rib assembly .
PART 
NUMBER QTY NOMENCLATURE ALTERNATE PART NUMBER
AN960-616L 2 Washer
CR2245-4-02 40 Rivet, Blind CR3245-4-02
CR3212-4-04 25 Rivet, Blind
CR3213-4-02 20 Rivet, Blind
CR3214-4-04 40 Rivet, Blind
CR3242-4-01 32 Rivet, Blind
CR3242-4-02 145 Rivet, Blind
CR3242-4-03 15 Rivet, Blind
CR3242-4-04 2 Rivet, Blind
CR3243-4-01 11 Rivet, Blind
CR3243-4-04 3 Rivet, Blind
MS14145-4 1 Nut MS14145L4
MS20426B3-5 10 Rivet
MS20426B3-7 10 Rivet MS20426B3-7N
MS20426B4-5 1 Rivet
MS20470AD5-5 2 Rivet
MS20470B3-5 30 Rivet
MS20470B3-7 30 Rivet
MS20470B4-5 2 Rivet
MS24665-134 1 Cotter Pin
NAS1097AD4-2 4 Rivet, Shear Head
NAS1097AD4-4 17 Rivet, Shear Head
NAS1097AD4-5 6 Rivet, Shear Head
NAS1097AD5-5 10 Rivet, Shear Head
NAS1097B3-5 8 Rivet, Shear Head
NAS1097B3-7 8 Rivet, Shear Head

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Service Bulletin
NOTE: Some hardware comes in pre-packaged quantities. When that occurs, the quantity in
the kit will be more than the quantity in the parts list.
(8) The 2381000-821 kit is effective for all aircraft and contains the parts as follows:
NOTE: The 2381000-821 kit replaces the RH inboard flap roller rib and nose roller support rib
assembly .
NAS334CP16 1 Bolt
NAS43DD4-30 1 Spacer
NAS43DD4-30N 
or 
NAS43DD4-30FC
NAS76A4-20 1 Bushing
2325000-13 1 Roller, Nose
2381000-815 1 Rib Assembly, LH Inboard Nose Roller Support
6025028-801 1 Rib, LH Inboard Flap Roller
PART 
NUMBER QTY NOMENCLATURE ALTERNATE PART NUMBER
AN960-616L 2 Washer
CR2245-4-02 40 Rivet, Blind CR3245-4-02
CR3212-4-04 25 Rivet, Blind
CR3213-4-02 20 Rivet, Blind
CR3214-4-04 40 Rivet, Blind
CR3242-4-01 32 Rivet, Blind
CR3242-4-02 145 Rivet, Blind
CR3242-4-03 15 Rivet, Blind
CR3242-4-04 2 Rivet, Blind
CR3243-4-01 11 Rivet, Blind
CR3243-4-04 3 Rivet, Blind
MS14145-4 1 Nut MS14145L4
MS20426B3-5 10 Rivet
MS20426B3-7 10 Rivet
PART 
NUMBER QTY NOMENCLATURE ALTERNATE PART NUMBER

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Service Bulletin
NOTE: Some hardware comes in pre-packaged quantities. When that occurs,
the quantity in the kit will be more than the quantity in the parts list.
MS20426B-4-5 1 Rivet
MS20470AD5-5 2 Rivet
MS20470B3-5 30 Rivet
MS20470B3-7 30 Rivet MS20426B3-7N
MS20470B4-5 2 Rivet
MS24665-134 1 Cotter Pin
NAS1097AD4-2 4 Rivet, Shear Head
NAS1097AD4-4 17 Rivet, Shear Head
NAS1097AD4-5 6 Rivet, Shear Head
NAS1097AD5-5 10 Rivet, Shear Head
NAS1097B3-5 8 Rivet, Shear Head
NAS1097B3-7 8 Rivet, Shear Head
NAS334CP16 1 Bolt
NAS43DD4-30 1 Spacer
NAS43DD4-30N 
or 
NAS43DD4-30FC
NAS76A4-20 1 Bushing
2325000-13 1 Roller, Nose
2381000-816 1 Rib Assembly, RH Inboard Nose Roller Support
6025028-802 1 Rib, RH Inboard Flap Roller
PART 
NUMBER QTY NOMENCLATURE ALTERNATE PART NUMBER

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Service Bulletin
(9) The 2381000-817 kit is effective for all aircraft and contains the parts as follows:
NOTE: One 2381000-817 kit is required to rig and functional test each
flap and contains parts for flap alignment of only one (1) flap.
NOTE: Some hardware comes in pre-packaged quantities. When that occurs,
the quantity in the kit will be more than the quantity in the parts list.
PART NUMBER QTY NOMENCLATURE ALTERNATE PART NUMBER
NAS1149C0716R 4 Washer
NAS1149C0616R 4 Washer
AN960-10 8 Washer
AN960-10L 8 Washer
AN960-416 6 Washer
AN960-416L 6 Washer
AN960-616 4 Washer
AN960-616L 12 Washer
AN960-716 4 Washer
AN960-716L 12 Washer
AN960-PD416 3 Washer
CF-1-S-CP 4 Cam Follower
CF-7/8-S-CP 4 Cam Follower
MS20364-720 4 Nut MS20364-720C
MS21042L6 4 Nut
2322513-1 8 Button
2322513-2 8 Button
2614068-811 1 Modification Placard

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B. Parts Removed List
(1) If the 2381000-802 kit is to be installed, remove the following parts:
(2) If the 2381000-804 kit is to be installed, remove the following parts:
(3) If the 2381000-809 kit is to be installed, remove the following parts:
(4) If the 2381000-810 kit is to be installed, remove the following parts:
PART 
NUMBER QTY NOMENCLATURE DISPOSITION EFFECTIVITY REPLACED BY
2625024-5 1 Outboard Flap Track Roller Fitting Destroy All 6025021-801
PART 
NUMBER QTY NOMENCLATURE DISPOSITION EFFECTIVITY REPLACED BY
2625024-6 1 Outboard Flap Track Roller Fitting Destroy All 6025021-802
PART 
NUMBER QTY NOMENCLATURE DISPOSITION EFFECTIVITY REPLACED BY
2625023-7 
or
2625023-11 
or
2625023-17
1 Inboard Flap Track Roller Fitting Destroy When Installed 6025022-809
PART 
NUMBER QTY NOMENCLATURE DISPOSITION EFFECTIVITY REPLACED BY
2625023-8 
or
2625023-12 
or
2625023-18
1 Inboard Flap Track Roller Fitting Destroy When Installed 6025022-810

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(5) If the 2381000-818 kit is to be installed, remove the following parts:
(6) If the 2381000-819 kit is to be installed, remove the following parts:
PART 
NUMBER QTY NOMENCLATURE DISPOSITION EFFECTIVITY REPLACED BY
2625015-47 
or 
2625015-71 
or
2625015-75
1 Outboard Leading Edge Rib Destroy When Installed 6025028-803
2325010-197 1 Backing Plate Destroy All 6025028-803
2325010-243 1 Nose Roller Support Destroy All 6025028-803
2325010-291 
or
2325010-331
1 Nose RollerSupport Destroy When Installed 2381000-813
2625015-34 
or 
2625015-69
1 Roller Support Destroy When Installed 2381000-813
2325010-241 1 Rub Strip Destroy All 2381000-813
PART 
NUMBER QTY NOMENCLATURE DISPOSITION EFFECTIVITY REPLACED BY
2625015-48 
or
2625015-72 
or 
2625015-76
1 Outboard Leading Edge Rib Destroy When Installed 6025028-804
2325010-197 1 Backing Plate Destroy All 6025028-804
2325010-243 1 Nose Roller Support Destroy All 6025028-804
2325010-292 
or 
2325010-332
1 Nose RollerSupport Destroy When Installed 2381000-814
2625015-35 
or
2625015-70
1 Roller Support Destroy When Installed 2381000-814
2325010-241 1 Rub Strip Destroy All 2381000-814

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(7) If the 2381000-820 kit is to be installed, remove the following parts:
(8) If the 2381000-821 kit is to be installed, remove the following parts:
PART 
NUMBER QTY NOMENCLATURE DISPOSITION EFFECTIVITY REPLACED BY
2625015-29 
or
2625015-67 
or
2625015-73
1 Inboard Leading Edge Rib Destroy When Installed 6025028-801
2325010-242 
or
2325010-303
1 Nose Roller Support Destroy When Installed 6025028-801
2325010-248 
or
2325010-304
1 Reinforcement Rib Destroy When Installed 6025028-801
2325010-115 
or
2325010-329
1 Nose RollerSupport Destroy When Installed 2381000-815
2325010-165 
or
2325010-333
1 Roller Support Destroy When Installed 2381000-815
2325010-241 1 Rub Strip Destroy All 2381000-815
PART 
NUMBER QTY NOMENCLATURE DISPOSITION EFFECTIVITY REPLACED BY
2625015-30 
or
2625015-68 
or
2625015-74
1 Inboard Leading Edge Rib Destroy When Installed 6025028-802
2325010-303 1 Nose Roller Support Destroy All 6025028-802
2325010-305 1 Reinforcement Rib Destroy All 6025028-802
2325010-116 
or
2325010-330
1 Nose RollerSupport Destroy When Installed 2381000-816

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LEARJET 55
Service Bulletin
3. Accomplishment Instructions
A. Gain Access
(1) Extend the flaps. (Refer to FAA approved Learjet Flight Manual.)
(2) Disconnect external electrical power and the main and emergency batteries from the aircraft.
(Refer to Chapter 24 of the Maintenance Manual .)
B. Modification of Aircraft
NOTE: For dimensions defined without specific tolerance information, refer to Paragraph 3.G. for
standard tolerances.
(1) Aircraft that have previously accomplished the modifications, at all four locations, in accordance
with Service Bulletin 55-27-32, "Inspection/Installation of Flap Structure Components" Basic issue
dated November 12, 2003, or Rev 1, dated December 16, 2003, or Rev 2, dated May 28, 2004, or
Rev 3, dated J une 7, 2010, or Re v 4, dated A ugust 26, 2013 , proceed to Step 3.B.(13).
(2) On aircraft that have modified inboard/outboard flap roller ribs or the inboard/outboard nose roller
support rib assemblies, or the inboard/outboard flap track roller fittings on LH or RH sides, other
than in accordance with Service Bulletin 55-27-32, as stated in the step above, contact Learjet for
repair instructions. (Refer to the title page of this document for contact information.)
(3) Aircraft that have not previously accomplished the modifications, at all four locations, as stated in
Step 3.B.(1),r emove flaps from aircraft (Refer to Chapter 27 of the Maintenance Manual .).
(4) On aircraft that have modified both LH and RH inboard flap roller ribs and the inboard nose roller
support rib assemblies in accordance with Service Bulletin 55-27-32, as stated in Step 3.B.(1)
above, proceed to Step 3 .B.(6).
(5) On aircraft that have not modified the inboard flap roller ribs and the inboard nose roller support rib
assemblies in accordance with Service Bulletin 55-27-32, as stated in Step 3.B.(1), above, install
the -820 (LH) and/or -821 (RH) kits as follows: (See Figure 1 .) The nose roller support rib assem-
blies and the flap roller ribs must be replaced together. Both the LH and RH locations must contain
all the modified components required.
(a) Drill out rivets, as required, to allow the lower trailing edge skins to be peeled back to gain
access to the spars and the rib attaching rivets. (Refer to Chapter 51 of the Structural Repair
Manual.) (See Figure 4 for approximate rivet locations.)
(b) T rim the leading edge skins to provide clearance for the replacement nose roller support rib
assemblies. (See Figure 1.)
(c) Maintain proper minimum edge distance for all rivets when trimming the leading edge skin cut-
outs. (Refer to Chapter 51 of the Structural Repair Manual , Section 51-40-02, paragraph
1.D.(1).)
(d) Prefit the new flap roller ribs and the new nose roller support ribs to the flap assemblies and
match drill to existing holes in skin and structure.
(e) Apply chemical film and epoxy primer to bare areas. (Refer to Chapter 20 of the Maintenance
Manual.)
(f) Solvent clean mating surfaces. (Refer to Chapter 20 of the Maintenance Manual .)
2325010-166 
or
2325010-334
1 Roller Support Destroy When Installed 2381000-816
2325010-241 1 Rub Strip Destroy All 2381000-816
PART 
NUMBER QTY NOMENCLATURE DISPOSITION EFFECTIVITY REPLACED BY

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LEARJET 55
Service Bulletin
(g) Install the flap roller ribs and the nose roller support ribs with the new rivets supplied in con-
junction with the adhesive bonding method as follows: (See Figure 1.)
NOTE: It is acceptable to use Class II adhesive as an alternate bonding method. (Refer to
Chapter 20 of the Maintenance Manual .)
1) Remove the Hysol EA 9602.3 adhesive film from refrigerated storage and allow to warm to
room temperature, or until moisture no longer condenses on the container, before opening
for use.
2) Remove the liner from adhesive film.
3) Apply one layer of adhesive film to the upper faying surfaces. Use care to prevent air
entrapment under film.
4) Heat tack the adhesive to hold in place. T emperature used for heat tacking shall not
exceed 150° F [65° C].
5) Remove the protective backing from the applied film.
6) Use an ice pick or similar tool to punch through adhesive film at each rivet hole.
7) Install the flap roller ribs and the nose roller support ribs with the new rivets supplied.
(Refer to Chapter 51 of the Structural Repair Manual .)
8) After all modifications to flaps have been completed, cure the assemblies in a circulating
hot air oven at 260 (+20; -10) °F [126.7 (+11.1; -5.6) °C] for 65 (+40; -5) minutes. Assem-
blies must be cured within two (2) weeks with ambient temperature of 90° F [32° C] or
within four (4) weeks with ambient temperature of 77° F [25° C].
(6) On aircraft that have modified both LH and RH outboard flap roller ribs and the outboard nose
roller support rib assemblies in accordance with Service Bulletin 55-27-32, as stated in the Step
3.B.(1) of this document , proceed to Step 3.B.(8).
(7) On aircraft that have not modified the outboard flap roller ribs and the outboard nose roller support
rib assemblies in accordance with Service Bulletin 55-27-32, as stated in the Step 3.B.(1) of this
document, install the -818 (LH) and/or -819 (RH) kits as follows: (See Figure 2 .) The nose roller
support rib assemblies and the flap roller ribs must be replaced together. Both the LH and RH loca-
tions must contain all the modified components required.
(a) Drill out rivets, as required, to allow the lower trailing edge skin to be peeled back to gain
access to the spar and the rib attaching rivets. (Refer to Chapter 51 of the Structural Repair
Manual.) (See Figure 4 for approximate rivet locations.)
(b) T rim the leading edge skin to provide clearance for the replacement nose roller support rib
assembly . (SeeFigure 2.)
(c) Maintain proper minimum edge distance for all rivets when trimming the leading edge skin cut-
outs. (Refer to Chapter 51 of the Structural Repair Manual , Section 51-40-02, paragraph
1.D.(1).)
(d) Prefit the new flap roller ribs and the new nose roller support ribs to the flap assemblies and
match drill to existing holes in skin and structure.
(e) Apply chemical film and epoxy primer to bare areas. (Refer to Chapter 20 of the Maintenance
Manual.)
(f) Solvent clean mating surfaces. (Refer to Chapter 20 of the Maintenance Manual .)
(g) Install the flap roller ribs and the nose roller support ribs with the new rivets supplied in con-
junction with the adhesive bonding method as follows: (See Figure 2.)
NOTE: It is acceptable to use Class II adhesive as an alternate bonding method. (Refer to
Chapter 20 of the Maintenance Manual .)
1) Remove the Hysol EA 9602.3 adhesive film from refrigerated storage and allow to warm to
room temperature, or until moisture no longer condenses on the container, before opening
for use.

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LEARJET 55
Service Bulletin
2) Remove the liner from adhesive film.
3) Apply one layer of adhesive film to the upper faying surfaces. Use care to prevent air
entrapment under film.
4) Heat tack the adhesive to hold in place. T emperature used for heat tacking shall not
exceed 150° F [65° C].
5) Remove the protective backing from the applied film.
6) Use an ice pick or similar tool to punch through adhesive film at each rivet hole.
7) Install the flap roller ribs and the nose roller support ribs with the new rivets supplied.
(Refer to Chapter 51 of the Structural Repair Manual .)
8) After all modifications to flaps have been completed, cure the assemblies in a circulating
hot air oven at 260 (+20; -10) °F [126.7 (+11.1; -5.6) °C] for 65 (+40; -5) minutes. Assem-
blies must be cured within two (2) weeks with ambient temperature of 90° F [32° C] or
within four (4) weeks with ambient temperature of 77° F [25° C].
(8) On aircraft that have modified both LH and RH inboard flap track roller fittings in accordance with
Service Bulletin 55-27-32, as stated in the Step 3.B.(1) of this document, proceed to Step 3.B. (10).
(9) On aircraft that have not modified the inboard flap track roller fittings in accordance with Service
Bulletin 55-27-32, as stated in the Step 3.B.(1) of this document, install the -809 (LH) and/or -810
(RH) kits as follows. (See Figure 1 .) Both the LH and RH locations must contain all the modified
components required.
CAUTION: INSTALL RIVETS IN THE FLAP TRACK ROLLER FITTING USING THE
SQUEEZE TECHNIQUE. THE FLAP TRACK ROLLER FITTING MAY BE DAM-
AGED USING OTHER TYPES OF RIVET INSTALLATION.
(a) Drill out rivets and remove the flap track roller fittings. (See Figure 1 .) (Refer to Chapter 51 of
the Structural Repair Manual .)
(b) Prefit the new flap track roller fittings to the flap assemblies and match drill to existing holes in
skin and structure.
(c) Apply chemical film and epoxy primer to bare areas. (Refer to Chapter 20 of the Maintenance
Manual.)
(d) Solvent clean mating surfaces. (Refer to Chapter 20 of the Maintenance Manual .)
CAUTION: INSTALL RIVETS IN THE FLAP TRACK ROLLER FITTING USING THE
SQUEEZE TECHNIQUE. THE FLAP TRACK ROLLER FITTING MAY BE DAM-
AGED USING OTHER TYPES OF RIVET INSTALLATION.
(e) Install the inboard flap track roller fittings with the new rivets supplied in conjunction with the
adhesive bonding method as follows: (See Figure 1.)
NOTE: It is acceptable to use Class II adhesive as an alternate bonding method. (Refer to
Chapter 20 of the Maintenance Manual .)
1) Remove the Hysol EA 9602.3 adhesive film from refrigerated storage and allow to warm to
room temperature, or until moisture no longer condenses on the container, before opening
for use.
2) Remove the liner from adhesive film.
3) Apply one layer of adhesive film to the upper faying surfaces. Use care to prevent air
entrapment under film.
4) Heat tack the adhesive to hold in place. T emperature used for heat tacking shall not
exceed 150° F [65° C].
5) Remove the protective backing from the applied film.
6) Use an ice pick or similar tool to punch through adhesive film at each rivet hole.

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LEARJET 55
Service Bulletin
CAUTION: INSTALL RIVETS IN THE FLAP TRACK ROLLER FITTING USING THE
SQUEEZE TECHNIQUE. THE FLAP TRACK ROLLER FITTING MAY BE
DAMAGED USING OTHER TYPES OF RIVET INSTALLATION.
7) Install the new flap track roller fittings with the new rivets supplied. (Refer to Chapter 51 of
the Structural Repair Manual .)
8) After all modifications to flaps have been completed, cure the assemblies in a circulating-
air oven at 260 (+20; -10) °F [126.7 (+11.1; -5.6) °C] for 65 (+40; -5) minutes. Assemblies
must be cured within two (2) weeks with ambient temperature of 90° F [32° C] or within
four (4) weeks with ambient temperature of 77° F [25° C].
(10) On aircraft that have modified both LH and RH outboard flap track roller fittings, in accordance with
Service Bulletin 55-27-32, as stated in the Step 3.B.(1) of this document, proceed to Step 3.B .(12).
(11) On aircraft that have not modified the outboard flap track roller fittings in accordance with Service
Bulletin 55-27-32, as stated in the Step 3.B.(1) of this document, install the -802 (LH) and/or -804
(RH) kits as follows. (See Figure 2 .) Both the LH and RH locations must contain all the modified
components required.
CAUTION: INSTALL RIVETS IN THE FLAP TRACK ROLLER FITTING USING THE
SQUEEZE TECHNIQUE. THE FLAP TRACK ROLLER FITTING MAY BE DAM-
AGED USING OTHER TYPES OF RIVET INSTALLATION.
(a) Drill out rivets and remove the flap track roller fittings. (See Figure 2 .) (Refer to Chapter 51 of
the Structural Repair Manual .)
(b) Prefit the new flap track roller fittings to the flap assemblies and match drill to existing holes in
skin and structure.
(c) Apply chemical film and epoxy primer to bare areas. (Refer to Chapter 20 of the Maintenance
Manual.)
(d) Solvent clean mating surfaces. (Refer to Chapter 20 of the Maintenance Manual .)
CAUTION: INSTALL RIVETS IN THE FLAP TRACK ROLLER FITTING USING THE
SQUEEZE TECHNIQUE. THE FLAP TRACK ROLLER FITTING MAY BE DAM-
AGED USING OTHER TYPES OF RIVET INSTALLATION.
(e) Install the outboard flap track roller fittings with the new rivets supplied in conjunction with the
adhesive bonding method as follows:. (See Figure 2.)
NOTE: It is acceptable to use Class II adhesive as an alternate bonding method. (Refer to
Chapter 20 of the Maintenance Manual .)
1) Remove the Hysol EA 9602.3 adhesive film from refrigerated storage and allow to warm to
room temperature, or until moisture no longer condenses on the container, before opening
for use.
2) Remove the liner from adhesive film.
3) Apply one layer of adhesive film to the upper faying surfaces. Use care to prevent air
entrapment under film.
4) Heat tack the adhesive to hold in place. T emperature used for heat tacking shall not
exceed 150° F [65° C].
5) Remove the protective backing from the applied film.
6) Use an ice pick or similar tool to punch through adhesive film at each rivet hole.

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LEARJET 55
Service Bulletin
CAUTION: INSTALL RIVETS IN THE FLAP TRACK ROLLER FITTING USING THE
SQUEEZE TECHNIQUE. THE FLAP TRACK ROLLER FITTING MAY BE
DAMAGED USING OTHER TYPES OF RIVET INSTALLATION.
7) Install the new flap track roller fittings with the new rivets supplied. (Refer to Chapter 51 of
the Structural Repair Manual .)
8) After all modifications to flaps have been completed, cure the assemblies in a circulating-
air oven at 260 (+20; -10) °F [126.7 (+11.1; -5.6) °C] for 65 (+40; -5) minutes. Assemblies
must be cured within two (2) weeks with ambient temperature of 90° F [32° C] or within
four (4) weeks with ambient temperature of 77° F [25° C].
(12) Install th e skins with the rivets supplied in conjunction with the adhesive bonding method as fol-
lows: (See Figure 4.)
NOTE: It is acceptable to use Class II adhesive as an alternate bonding method. (Refer to
Chapter 20 of the Maintenance Manual .)
(a) Apply chemical film and epoxy primer to bare areas. (Refer to Chapter 20 of the Maintenance
Manual.)
(b) Solvent clean mating surfaces. (Refer to Chapter 20 of the Maintenance Manual .)
(c) Remove the Hysol EA 9602.3 adhesive film from refrigerated storage and allow to warm to
room temperature, or until moisture no longer condenses on the container, before opening for
use.
(d) Remove the liner from adhesive film.
(e) Apply one layer of adhesive film to the faying surfaces. Use care to prevent air entrapment
under film.
(f) Heat tack the adhesive to hold in place. T emperature used for heat tacking shall not exceed
150° F [65° C].
(g) Remove the protective backing from the applied film.
(h) Use an ice pick or similar tool to punch through adhesive film at each rivet hole.
(i) Install the flap skin with the new rivets supplied. (Refer to Chapter 51 of the Structural Repair
Manual.)
(j) After all modifications to flaps have been completed, cure the assemblies in a circulating-air
oven at 260 (+20; -10) °F [126.7 (+11.1; -5.6) °C] for 65 (+40; -5) minutes. Assemblies must be
cured within two (2) weeks with ambient temperature of 90° F [32° C] or within four (4) weeks
with ambient temperature of 77° F [25° C].
(13) Apply the modification placard to the flap, complete the information , and clear coat the modifica-
tion placard, supplied in the -817 kit as follows: (See Figure 4, View B-B.)
(a) Solvent clean area of the flap location where the placard is to be applied. Make sure it is clean
and dry before the placard is applied. (Refer to Chapter 20 of the Maintenance Manual .)
(b) Apply the placard to the flap.
(c) Solvent clean the placard. Make sure the placard is clean and dry before it is marked.
(Refer to Chapter 20 of the Maintenance Manual .)
(d) Use an indelible marker to write "SB 55-27-41" on the placard. (Kit number is not required,
leave blank.)
CAUTION: MAKE SURE TO PAY CLOSE ATTENTION TO ALL MANUFACTURER WARN-
INGS, MIXING, APPLICATION, DISPOSAL INSTRUCTIONS AND CURE
TIMES ON THE PRODUCT CONTAINER(S) IN ORDER TO AVOID PERSONAL
INJURY AND/OR COMPROMISED QUALITY OF THE END PRODUCT.
(e) Placard markings must be over coated with clear polyurethane protective coating as follows:.

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LEARJET 55
Service Bulletin
1) Mix catalyst and components as directed on the containers. Mix only the amount needed
and stir thoroughly .
NOTE: If thinning is required, a maximum of one part thinner may be added to the
mixed material. Stir thoroughly .
2) Apply clear polyurethane protective coating with a small throw-away paint brush, as
required to achieve a uniform dry film thickness of 1.5 to 2.5 mils.
NOTE: Cure time to handle is 45 minutes at 75° F or 15 Minutes at 150° F .
(14) On aircraft that did not remove flaps f or modification, proceed to Step 3.D.
(15) On aircraft that remo ved flaps f or modification, do as follows.
(a) Replace cam followers (provided in the -817 kit). (See Figure 3.)
(b) Replace the cam follower washers common to the stud (provided in the -817 kit).
(See Figure 3.)
(c) Install the flaps on the aircraft. (Refer to Chapter 27 of the Maintenance Manual .)
(16) Do not perform the Functional T est of Flap System at this time.
C. Functional T est/Operational Check.
(1) Inspect the alignment of the LH and RH flaps as follows:
(a) Connect the batteries to the aircraft.
(b) Extend and retract the flaps. (Refer to Chapter 27 of the Maintenance Manual .)
CAUTION: NOSE ROLLER TRACKS MUST NOT TOUCH THE FLAP ROLLER RIBS OR
THE NOSE ROLLER SUPPORT RIBS, THROUGHOUT THE COMPLETE
OPERATION OF THE FLAPS, EVEN WHILE PUSHING HARD, INBOARD OR
OUTBOARD ON THE FLAPS.
(c) Make sure that the inboard and outboard nose roller tracks stay approximately centered on the
nose rollers throughout the complete operation of the flaps.
(2) On aircraft with correct flap alignment, proceed to Step 3.C.(4) for the Functional T esting of Flap
System.
CAUTION: MAKE SURE TO MAINTAIN MINIMUM GAP REQUIREMENTS BETWEEN FUSE-
LAGE, FLAP, AND AILERON. (REFER TO CHAPTER 27 OF THE MAINTENANCE
MANUAL.)
(3) On aircraft with incorrect flap alignment, use components provided in the -817 kit(s) (as needed)
and make adjustments until the nose roller tracks no longer touch the flap roller ribs or the nose
roller support ribs. Make adjustments, as required, in the following order:
(a) Install any combination of cam follower buttons to tighten up and control the spanwise move-
ment of the flap. (See Figure 5.)
(b) Shim the cam follower buttons using one (1) washer under button as required. (See Figure 5.)
(c) Shim the cam followers using a maximum of two (2) washers per follower as required. (See
Figure 5.)
(d) If further adjustment is required, shim the nose roller track away from the flap track support fit-
ting with one (1) washer under each nose roller track bolt. (See Figure 6.)
(4) Do a Functional T est of Flap System. (Refer to Chapter 27 of the Maintenance Manual .)

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LEARJET 55
Service Bulletin
D. Return Aircraft to Airworthy Status
(1) Install any additional items removed for access.
E. Compliance Response Form
(1) Complete the compliance response form.
(2) Send the compliance response form to Learjet Inc. as soon as possible.
F . Aircraft Maintenance Records
(1) Complete the Aircraft Maintenance Records in accordance with the regulatory requirements of the
appropriate aircraft certification authority .
G. General Information
(1) The table below lists standard tolerances which shall apply to dimensions defined within the
instructions or illustrations of this document that do not have specified tolerances.
UNLESS OTHERWISE SPECIFIED
ALL TOLERANCES ARE AS FOLLOWS:
DECIMALS ANGLES
 0.0 ± 0.1 in [0.0 mm ± 2.54 mm]
0.00 ± 0.03 in [0.00 mm ± 0.76 mm]
0.000 ± 0.010 in [0.000 mm ± 0.254 mm] 
MACHINED FORMED
± 0°30’ ± 2 °

### Page 25 (OCR)

LEARJET 55
Service Bulletin
→f0000  7 FLAP  FLAP  FLAP
STATION  STATION  STATION
37.85  40.00  42.15
—
C  C
+  T
FLAP TRACK
ROLLER FITTING
6025022-809 - LH (-809 KIT)
6025022-810 - RH (-810 KIT)
(1 REQUIRED)
NOSE ROLLER SUPPORT
RIB ASSEMBLY
2381000-815 - LH (-820 KIT)
2381000-816 - RH (-821 KIT)
(1 REQUIRED)
FWD
FLAP ROLLER RIB
6025028-801 - LH (-820 KIT)
6025028-802 - RH (-821 KIT)
(1 REQUIRED)
B
COUNTERSINK 0.44 TO 0.45 in
[11.18 TO 11.43 mm] BY 100°
(MEW LOOKING DOWN AT FLAP, INBOARD NOSE ROLLER AREA
(LH SHOWN, RH OPPOSITE)
Detail A  K55-552732-001-01
Inboard Flap Track Roller Fitting, Flap Roller Rib, and Nose Roller Support Rib Replacement
Figure 1 (Sheet 1 of 4)
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### Page 26 (OCR)

LEARJET 55
Service Bulletin
0.125 in  0.30 A.C.
[3.175 mm]  WRP
RADIUS  (REF)
(2 PLACES)  0.48 A.C.
INBD FLAP
ROLLER RIB
(REF)
0.52 A.C.
0.90 in
(APPROX.)  [2.28 cm] →  0.25 A.C.
(SHOWING THE ADDITIONAL SKIN CUTOUT
REQUIRED FOR CLEARANCE FOR THE NEW FLAP ROLLER RIB)
(LH SHOWN, RH OPPOSITE)
View B-B
FLAP  FLAP  FLAP
STATION  STATION  STATION
37.85  40.00  42.15
D  D
FLAP TRACK  NOSE ROLLER SUPPORT  FLAP ROLLER RIB
ROLLER FITTING  RIB ASSEMBLY  6025028-801/802
6025022-809/-810  2381000-815/816  (REF)
(REF)  (REF)
(VIEW LOOKING AFT TOWARDS FLAP SPAR)
(LH SHOWN, RH OPPOSITE)
View C-C
K55-552732-001-02
Inboard Flap Track Roller Fitting, Flap Roller Rib, and Nose Roller Support Rib Replacement
Figure 1 (Sheet 2 of 4)
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### Page 27 (OCR)

LEARJET 55
Service Bulletin
NOSE ROLLER SUPPORT
2381000-815/-816
RIB ASSEMBLY  FLAP
(REF)  STA
42.15
FLAP
STA  - 0.625 in
37.70  [15.875 mm]  FLAP ROLLER RIB
6025028-801/-802
FLAP  (REF)
STA
40.00
FLAP TRACK
ROLLER FITTING  6025022-809/-810  FWD
(REF)
099
(VIEW LOOKING UP AT FLAP)
(LH SHOWN, RH OPPOSITE)
View D-D
K55-552732-001-03
Inboard Flap Track Roller Fitting, Flap Roller Rib, and Nose Roller Support Rib Replacement
Figure 1 (Sheet 3 of 4)
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### Page 28 (OCR)

LEARJET 55
Service Bulletin
FASTENER SYMBOL LEGEND
SYMBOL  DESCRIPTION  SYMBOL  DESCRIPTION  SYMBOL  DESCRIPTION
CR3213-5-03  CR3524-5-05 Rivet  CSR904B-5-7
(C Sink 100°)  (C'Sink 100°)
CR3242-4-02  (Head on Near Side)  (Head on Near Side)
(C'Sink 100°)
(Head on Near Side)  MS20470AD5-5  NAS1097AD4-2
(C'Sink 100°)
CR3242-4-03  NAS1097AD4-4  (Head on Near Side)
(C'Sink 100°)  (C'Sink 100°)
(Head on Near Side)  (Head on Near Side)  NAS1097AD5-5
(C'Sink 100°)
CR3242-4-04  NAS1097AD4-5  (Head on Near Side)
(C'Sink 100°)  (C'Sink 100°)
(Head on Near Side)  (Head on Near Side)
NAS1097AD4-7
CR3243-4-04  NAS1097AD4-5  (C'Sink 100°)
(2xC'Sink 100°)  (Head on Near Side)
CSR904B-5-5  (Double Flush)
(C'Sink 100°)  (Head on Near Side)
(Head on Near Side)
NOTES
Inspect skin perimeter for cracks (upper and lower).
Cutout approximately 1.50 x 0.50 in [38.10 x 12.70 mm] along contour.
Permissible to reinstall existing shims or fabricate new shims as necessary
to fill any voids between fitting and adjacent mating structure. Make from 2024-T3.
4.  Maintain proper edge margin for all rivets.
Acceptable to use CR3524-4-04 rivet if unable to squeeze NAS1097AD rivet (1 place only).
Install rivets in the flap attach fitting using the squeeze technique.
Bond upper surface of fitting with HYSOL EA 9602.3 adhesive film. (Acceptable to bond
with Class Il adhesive as an alternate.) (Refer to Learjet Maintenance Manual, Chapter 20.)
8.  Install rivets wet with Class Il adhesive.
(Refer to Learjet Maintenance Manual, Chapter 20.)
Acceptable to notch or trim the top aft edge of rib to clear rivet if unable to
install with proper mininum edge distance.
Install CR3243-5-03 rivets in lieu of CR3213-5-03 on aircraft equipped
with flaps modified by SSK55-512.
Install one each AN3-5A bolt, AN960-10L washer, and MS21042-L3 nut
three places on aircraft with flaps modified by SSK55-512.
K55-552732-001-04
Inboard Flap Track Roller Fitting, Flap Roller Rib, and Nose Roller Support Rib Replacement
Figure 1 (Sheet 4 of 4)
Basic Issue: Sep 11/17  THIS PUBLICATION IS AVAILABLE AT:  SB 55-27-41
https://my.businessaircraft.bombardier.com  Recommended
Page 28 of 42

### Page 29 (OCR)

LEARJET 55
Service Bulletin
FLAP  FLAP  FLAP
STATION  STATION  STATION
104.20  106.15  108.10
C
FWD
FLAP TRACK
ROLLER FITTING
6025021-801 - LH (-802 KIT)
6025021-802 - RH (-804 KIT)
(1 REQUIRED)
FLAP ROLLER RIB
6025028-803 - LH (-818 KIT)
6025028-804 - RH (-819 KIT)
(1 REQUIRED)
NOSE ROLLER SUPPORT
RIB ASSEMBLY
2381000-813 - LH (-818 KIT)
2381000-814 - RH (-819 KIT)
(1 REQUIRED)
B
COUNTERSINK 0.44 TO 0.45 in
[11.18 TO 11.43 mm] BY 100°
(MIEW LOOKING DOWN AT FLAP, OUTBOARD NOSE ROLLER AREA
(LH SHOWN, RH OPPOSITE)
Detail A
K55-552732-002-01
Outboard Flap Track Roller Fitting, Flap Roller Rib, and Nose Roller Support Rib Replacement
Figure 2 (Sheet 1 of 4)
Basic Issue: Sep 11/17  THIS PUBLICATION IS AVAILABLE AT:  SB 55-27-41
https://my.businessaircraft.bombardier.com  Recommended
Page 29 of 42

### Page 30 (OCR)

LEARJET 55
Service Bulletin
0.125 in
[3.175 mm|
RADIUS
(2 PLACES)
0.30 A.C.
WRP
(REF)
0.30 A.C.
INBD FLAP
ROLLER RIB
(REF)
+0.40 A.C.
41 060
0.30 A.C.
(SHOWING THE ADDITIONAL SKIN CUTOUT)
(REQUIRED FOR CLEARANCE FOR THE NEW FLAP ROLLER RIB)
(LH SHOWN, RH OPPOSITE)
View B-B
FLAP  FLAP
NOTES  STATION  STATION
106.15  108.10
FLAP ROLLER RIB  NOSE ROLLER SUPPORT  FLAP TRACK
6025028-803/804  RIB ASSEMBLY  ROLLER FITTING
(REF)  2381000-813/814  6025021-801/-802
(REF)  (REF)
(VIEW LOOKING AFT TOWARDS FLAP SPAR)
(LH SHOWN, RH OPPOSITE)
View C-C
K55-552732-002-02
Outboard Flap Track Roller Fitting, Flap Roller Rib, and Nose Roller Support Rib Replacement
Figure 2 (Sheet 2 of 4)
Basic Issue: Sep 11/17  THIS PUBLICATION IS AVAILABLE AT:  SB 55-27-41
https://my.businessaircraft.bombardier.com  Recommended
Page 30 of 42

### Page 31 (OCR)

LEARJET 55
Service Bulletin
FLAP
STA
104.20  FLAP
STA
FLAP ROLLER RIB  6025028-803/804  0.625 in  108.25
(REF)  - [15.88 mm]
FLAP
STA  +  NOSE ROLLER SUPPORT
106.15  RIB ASSEMBLY
+  - 2381000-813/814
(REF)
FLAP TRACK
ROLLER FITTING
6025021-801/802
(REF)
FWD
(VIEW LOOKING UP AT FLAP)
(LH SHOWN, RH OPPOSITE)
View D-D
K55-552732-002-03
Outboard Flap Track Roller Fitting, Flap Roller Rib, and Nose Roller Support Rib Replacement
Figure 2 (Sheet 3 of 4)
Basic Issue: Sep 11/17  THIS PUBLICATION IS AVAILABLE AT:  SB 55-27-41
https://my.businessaircraft.bombardier.com  Recommended
Page 31 of 42

### Page 32 (OCR)

LEARJET 55
Service Bulletin
FASTENER SYMBOL LEGEND
SYMBOL  DESCRIPTION  SYMBOL  DESCRIPTION  SYMBOL  DESCRIPTION
CSR904B-5-7  CSR904B-5-4
CR3213-5-03  (C'Sink 100°)  (C'Sink 100°)
CR3242-4-02  (Head on Near Side)  (Head on Near Side)
(C'Sink 100°)  CR3524-5-05 Rivet  CSR904B-5-5
(Head on Near Side)  (C'Sink 100°)  (C'Sink 100°)
CR3242-4-03  (Head on Near Side)  (Head on Near Side)
(C'Sink 100°)  NAS1097AD4-5
(Head on Near Side)  (C Sink Both Sides 100°)  (Head on Near Side)  a  NAS1097AD4-7  (C Sink 100°)
CR3242-4-04  (Head on Near Side)
(C'Sink 100°)  NAS1097AD4-5
(Head on Near Side)  (C'Sink 100°)  (Head on Near Side)  MS20470AD5-5
CSR904B-5-3  NAS1097AD5-5
(Head on Near Side)  (C'Sink 100°)  •  (2xC'Sink 100°)  (Double Flush)  CR3243-4-04
(Head on Near Side)
NOTES
Trim this edge, if required, for clearance.
Inspect skin perimeter for cracks (upper and lower).
Cutout approximately 1.50 x 0.50 in [38.10 x 12.70 mm] along contour.
4.  Maintain proper edge margin for all rivets.
Permissible to reinstall existing shims or fabricate new shims as necessary to fill
any voids between fitting and adjacent mating structure. Make from 2024-T3.
Install rivets in the flap attach fitting using the squeeze technique.
Bond upper surface of fitting with HYSOL EA9602.3 adhesive film. (Acceptable to bond
with Class I adhesive as an alternate.) (Refer to Learjet Maintenance Manual, Chapter 20.)
8.  Install rivets wet with Class Il adhesive.
(Refer to Learjet Maintenance Manual, Chapter 20.)
Acceptable to use CR3524-5-05 rivet if unable to squeeze CSR904B-5 rivet.
[o Installate  Acceptable to notch or trim the top aft edge of rib to clear rivet if unable to
Install with proper minimum edge distance.
New location. Center within group.
Install CR3243-5-03 rivets in lieu of CR3213-5-03 on aircraft equipped with flaps
modified by SSK55-512.
Install one each AN3-5A bolt, AN960-10L washer, and MS21042-L3 nut three places
with flaps modified by SSK55-512.
Continue trim line aft only as far as necessary to remove unused fastener hole in skin.
Plug this hole in skin if rivet falls in radius of fitting.  K55-552732-002-04
Outboard Flap Track Roller Fitting, Flap Roller Rib, and Nose Roller Support Rib Replacement
Figure 2 (Sheet 4 of 4)
Basic Issue: Sep 11/17  THIS PUBLICATION IS AVAILABLE AT:  SB 55-27-41
https://my.businessaircraft.bombardier.com  Recommended
Page 32 of 42

### Page 33

THIS PUBLICA TION IS AVAILABLE A T:
https://my.businessaircraft.bombardier.com
SB 55-27-41
Recommended
Page 33 of 42
Basic Issue: Sep 11/17
LEARJET 55
Service Bulletin
Replacement of the Cam Follower and Washer
Figure 3
CAM FOLLOWER
REPLACE WASHER
AND CAM
FOLLOWER
K60-602722-006-01

### Page 34 (OCR)

LEARJET 55
Service Bulletin
FLAP  STA  126.17  - 4
•
<
SKIN, LOWER  (REF)  4444444  (VIEW LOOKING UP AT BOTTOM SIDE OF FLAP)  (OUTBOARD FLAP TRACK AREA  (LH SHOWN, RH OPPOSITE)
Detail A
FLAP  STA  108.25
FLAP  STA  104.20
FWD
AINBD
K55-552732-004-01
Flap Lower Skin Rivet Location
Figure 4 (Sheet 1 of 4)
Basic Issue: Sep 11/17  THIS PUBLICATION IS AVAILABLE AT:  SB 55-27-41
https://my.businessaircraft.bombardier.com  Recommended
Page 34 of 42

### Page 35 (OCR)

LEARJET 55
Service Bulletin
MODIFICATION
RIB  PLACARD
2325010  (REF)  2614068-811  (1 REQUIRED)  ID PLATE  S-905  (REF)  A FWD
1.25 in
[31.75 mm]
(MODIFICATION PLACARD INSTALLATION)
(OUTBOARD END OF FLAP)
(LH SHOWN, RH OPPOSITE)
View B-B
K55-552732-004-02
Flap Lower Skin Rivet Location
Figure 4 (Sheet 2 of 4)
Basic Issue: Sep 11/17  THIS PUBLICATION IS AVAILABLE AT:  SB 55-27-41
https://my.businessaircraft.bombardier.com  Recommended
Page 35 of 42

### Page 36 (OCR)

LEARJET 55
Service Bulletin
- LAF  • •  •  FWD  AINBD
FLAP  (EFFECTIVE FOR AIRCRAFT 55-101, 55-105, 55-107 THRU 55-147, AND  THOSE AIRCRAFT WHICH HAVE BEEN MODIFIED PER LEARJET ENGINEERING 5584030)
‡+  •  (VIEW LOOKING UP AT BOTTOM SIDE OF FLAP)
(INBOARD FLAP TRACK AREA  (LH SHOWN, RH OPPOSITE)  Detail C
****  4 4
* # *  *******  *****#
#:
K55-552732-004-03
Flap Lower Skin Rivet Location
Figure 4 (Sheet 3 of 4)
Basic Issue: Sep 11/17  THIS PUBLICATION IS AVAILABLE AT:  SB 55-27-41
https://my.businessaircraft.bombardier.com  Recommended
Page 36 of 42

### Page 37 (OCR)

LEARJET 55
Service Bulletin
FASTENER SYMBOL LEGEND
SYMBOL  DESCRIPTION  SYMBOL  DESCRIPTION  SYMBOL  DESCRIPTION
CR3242-4-02  CR3242-4-04
•  (2xDimple 100°)  •  (C'Sink 100°)  MS20470B3-5
(Head on Near Side)  (Head on Near Side)
CR3242-4-02  (C Sink 100°)  (Dimple 100°)  CR3242-4-02  (3x Dimple 100°)  CR2245-4-02  (C'Sink 100°)
(Head on Near Side)  (Head on Near Side)  (Head on Near Side)
CR3242-4-03  CR3242-4-03  CR3213-4-02
(3xDimple 100°)  (Head on Near Side)  (C'Sink 100°)  (Head on Near Side)  (Head on Near Side)
NOTE
Bond all surfaces with HYSOL EA9602.3 adhesive film (acceptable to bond with Class II
adhesive as an alternate.) (Refer to Learjet Maintenance Manual, Chapter 20.)
K55-552732-004-4
Flap Lower Skin Rivet Location
Figure 4 (Sheet 4 of 4)
Basic Issue: Sep 11/17  THIS PUBLICATION IS AVAILABLE AT:  SB 55-27-41
https://my.businessaircraft.bombardier.com  Recommended
Page 37 of 42

### Page 38 (OCR)

LEARJET 55
Service Bulletin
INBOARD FLAP
ROLLER RIB
6025028-801/-802
(REF)
NOSE ROLLER SUPPORT
RIB ASSEMBLY
2381000-815/816  (REF)  E
WASHER  NOSE ROLLER TRACK  NOSE
AN960-10  (REP)  ROLLER
WASHER  OR AN960-10L  B  2325000-013
AN960-716L  (AS REQUIRED,  (REF)
(AS REQUIRED,  4 PLACES)
4 PLACES)
CAM FOLLOWER
CF-1-S-CP
(4 REQUIRED)
BUTTON,  WASHER
2322513-2  AN960-716
(1 REQUIRED,  NUT  Detail A
4 PLACES)  MS20364-720
(1 EACH REQUIRED,  INBOARD FLAP TRACK SUPPORT
4 PLACES)  BRACKET INSTALLATION
View B-B  (LH SHOWN, RH OPPOSITE)
NOTES
Only one (1) washer may be used to shim each cam button.
A maximum of two (2) washers may be used to shim each cam follower.
Button 2322513-1 may be used as an alternate for 2322513-2 as required.
If minimum of one thread does not extend past end on nut, use AN960-616L or AN960-716L
washer. If still less than one thread, use NAS1149C0616R or NAS1149C0716R washer. End
of stud shall extend no less than flush with end of nut.
Torque nut to 30 in-Ibs (3.38 Nm). If the cotter pin can not be installed, continue to increase the
torque while trying to install the cotter pin to a maximum of 50 in-ibs (5.64 Nm).  K55-552732-005-01
Flap Track Support Bracket with Allowable Shims
Figure 5 (Sheet 1 of 3)
Basic Issue: Sep 11/17  THIS PUBLICATION IS AVAILABLE AT:  SB 55-27-41
https://my.businessaircraft.bombardier.com  Recommended
Page 38 of 42

### Page 39 (OCR)

LEARJET 55
Service Bulletin
OUTBOARD
FLAP
ROLLER RIB
6025028-803/-804
(REF)
NOSE ROLLER
SUPPORT RIB
ASSEMBLY
2381000-813/814
E—  (REF)
NOSE ROLLER  -NOSE ROLLER TRACK
2325000-013  (REF)
(REF)
D
WASHER  WASHER
CAM FOLLOWER
AN960-10  AN960-616L
CF-7/8-S-CP
(4 REQUIRED)  OR AN960-10L  (AS REQUIRED,
(AS REQUIRED,  4 PLACES)
4 PLACES)
Detail C
OUTBOARD FLAP TRACK SUPPORT
BRACKET INSTALLATION
(LH SHOWN, RH OPPOSITE)
WASHER  • BUTTON
AN960-616  2322513-2
NUT  (1 REQUIRED,
MS21042L6  4 PLACES)
(1 EACH REQUIRED,
4 PLACES)  View D-D
K55_559730_005_02
Flap Track Support Bracket with Allowable Shims
Figure 5 (Sheet 2 of 3)
Basic Issue: Sep 11/17  THIS PUBLICATION IS AVAILABLE AT:  SB 55-27-41
https://my.businessaircraft.bombardier.com  Recommended
Page 39 of 42

### Page 40 (OCR)

LEARJET 55
Service Bulletin
2325000-013
NOSE ROLLER
NAS76A4-20  (1 REQUIRED)
BUSHING
(1 REQUIRED)
AN960-PD416
WASHER
(2 REQUIRED)
NAS334CP16
BOLT
(1 REQUIRED)
MS24665-134
COTTER PIN
(1 REQUIRED)
MS14145-4
NUT
(1 REQUIRED)
NAS43DD4-30
SPACER
AN960-616L
WASHERS
(2 REQUIRED)
Detail E
K55-552732-005-03
Flap Track Support Bracket with Allowable Shims
Figure 5 (Sheet 3 of 3)
Basic Issue: Sep 11/17  THIS PUBLICATION IS AVAILABLE AT:  SB 55-27-41
https://my.businessaircraft.bombardier.com  Recommended
Page 40 of 42

### Page 41 (OCR)

LEARJET 55
Service Bulletin
>
0000
NOSE
ROLLER
TRACK
(REF)
WASHER
AN960-416
OR
AN960-416L
(1 EACH, 3 PLACES
AS REQUIRED)
FLAP
TRACK
SUPPORT
FITTING
(REF)
Detail A
(INBOARD FLAP TRACK SUPPORT)
(LH SHOWN, RH OPPOSITE)
K55-552732-006-01
Flap Track with Shimmed Nose Track
Figure 6 (Sheet 1 of 2)
Basic Issue: Sep 11/17  THIS PUBLICATION IS AVAILABLE AT:  SB 55-27-41
https://my.businessaircraft.bombardier.com  Recommended
Page 41 of 42

### Page 42 (OCR)

LEARJET 55
Service Bulletin
NOSE
ROLLER
TRACK
(REF)
WASHER
AN960-416
OR
AN960-416L
(1 EACH, 3 PLACES
AS REQUIRED)
FLAP
TRACK
SUPPORT
FITTING
(REF)
Detail B
(OUTBOARD FLAP TRACK SUPPORT)
(LH SHOWN, RH OPPOSITE)
NOTES
Permissible to replace bolts with one size longer when necessary for proper nut engagement.
One washer may be used under each nose roller track bolt for flap rigging.
K55-552732-006-02
Flap Track with Shimmed Nose Track
Figure 6 (Sheet 2 of 2)
Basic Issue: Sep 11/17  THIS PUBLICATION IS AVAILABLE AT:  SB 55-27-41
https://my.businessaircraft.bombardier.com  Recommended
Page 42 of 42

### Page 43

SERVICE BULLETIN COMPLIANCE RESPONSE
It is necessary that Bombardier Learjet record aircraft having complied with
this Service Bulletin. Please fill in the Service Bulletin and aircraft information
below, sign and date the form in the space provided, fold on dotted lines, seal
with tape, and mail completed form to Bombardier Learjet Maintenance Engi-
neering. If mailed within the United States, this form may be mailed to Bom-
bardier Learjet Maintenance Engineering using business reply mail (see
reverse). This form may be faxed or emailed if preferred. (See mailing infor-
mation provided.)
WARRANTY - Completion of this response form is required in order to pro-
cess the warranty claim. Therefore, if a warranty allowance is provided in the
Service Bulletin, return a copy of this form with the warranty claim.
SMART PARTS - Completion of this response form is required in order to
remain, enroll, or re-enroll in the Smart Parts Program.
*An email will be opened addressed to 
Fracas and this form will be attached.
Mailing Information:
Bombardier Learjet
Maintenance Engineering
(MS #78) (FAX 316 946-2305)
fracas_usa@aero.bombardier.com
Customer Support
Learjet, Inc.
CLICK HERE TO EMAIL
Service Bulletin Information
SB Title: ___________________________________________________________________________________
Service Bulletin No. _______________________ Rev No. ____________ Date ________________________
Aircraft Information
Model _____________ Serial No. _____________ Flight Hours _______________ Landings ______________
Service Facility Information
Facility Incorporating Bulletin ___________________________________________________________________
Compliance Information
The above referenced Service Bulletin was complied with on the referenced serial number aircraft at the listed air-
craft flight hours/landings:
Actual hours to accomplish Service Bulletin: Acce ss _______ Modify_______ Test(s) _______ Restore ________
Name: (Please Print) ______________________________________________ Date _____________________
Email: __________________________________________________________
Comments

### Page 44

FOLD HERE LAST. SEAL WITH TAPE. DO NOT STAPLE.
ATTN: MAINTENANCE ENGINEERING (MS NO. 78)
LEARJET INC
PO BOX 7707
WICHITA, KS 67277-9801
POSTAGE WILL BE PAID BY ADDRESSEE
BUSINESS REPLY MAIL
PERMIT NO. 2928 WICHITA, KSFIRST-CLASS MAIL
FOLD HERE FIRST
NO POSTAGE
NECESSARY
IF MAILED
IN THE
UNITED STATES

### Page 45

UPON COMPLETION OF THE EVALUATION FORM, YO U MAY FAX TO (316) 946-8876 OR FOLD AND
RETURN TO ADDRESS ON THE REVERSE SIDE OR USE THE SUBMIT BUTTON AT THE TOP TO EMAIL IT.
SERVICE BULLETIN EVALUATION SHEET
YOUR COMMENTS WILL HELP US IMPROVE
OUR SERVICE BULLETINS
*An email will be opened addressed to the 
SB Group and this form will be attached.
CLICK HERE TO EMAIL
SERVICE BULLETIN: ____________________ REVISION: _________ DATED: ________________________
TITLE: ____________________________________________________________________________________
LEARJET CONTACT INFORMATION TELEPHONE:  (316) 946-2421 FACSIMILE: (316) 946-8876
Actual hours to accomplish Service Bulletin: Access: ______ Modify: _______ Test(s): ______ Restore: _______
PLEASE SUPPLY THE FOLLOWING: NAME: _____________________________________________
OPERATOR: ___________________________________ EMAIL: ____________________________________
AIRCRAFT: _________________________________________ TELEPHONE:  _________________________
POOR FAIR GOOD VERY 
GOOD
EXCELLENT
HOW EASY IS THE BULLETIN TO UNDERSTAND?
COMMENTS
DOES THE BULLETIN TELL YOU ALL YOU NEED TO KNOW 
ABOUT THE JOB?
COMMENTS
DO YOU THINK THE BULLETIN CONVEYS THE BEST WAY 
TO DO THE JOB?
COMMENTS
HOW REALISTIC ARE THE LABOR-HOUR ESTIMATES?
COMMENTS
WHAT IS YOUR APPRECIATION OF THE ILLUSTRATION(S), 
FIGURE(S) AND/OR KIT DRAWING(S)?
COMMENTS

### Page 46

FOLD HERE LAST. SEAL WITH TAPE. DO NOT STAPLE.
ATTN: TECHNICAL PUBLICATIONS (MS NO. 53)
LEARJET INC
PO BOX 7707
WICHITA, KS 67277-9801
POSTAGE WILL BE PAID BY ADDRESSEE
BUSINESS REPLY MAIL
PERMIT NO. 2928 WICHITA, KSFIRST-CLASS MAIL
FOLD HERE FIRST
NO POSTAGE
NECESSARY
IF MAILED
IN THE
UNITED STATES

---
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